Six degree of freedom aerial vehicle having reconfigurable wings

ABSTRACT

Various reconfigurations of wing sections of a ring wing of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, one or more wing sections may be modified to maintain control and safety of the aerial vehicle. In example embodiments, positions, angular orientations, and/or pitches of one or more wing sections may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

CROSS-REFERENCE TO RELATED APPLICATION

This application is related to U.S. application Ser. No. 15/435,121, filed Feb. 16, 2017, entitled “Six Degree of Freedom Aerial Vehicle with a Ring Wing,” which is incorporated herein by reference in its entirety.

BACKGROUND

Unmanned vehicles, such as unmanned aerial vehicles (“UAV”), ground and water based automated vehicles, are continuing to increase in use. For example, UAVs are often used by hobbyists to obtain aerial images of buildings, landscapes, etc. Likewise, unmanned ground based units are often used in materials handling facilities to autonomously transport inventory within the facility. While there are many beneficial uses of these vehicles, balancing the tightly coupled vehicle performance parameters of stability, maneuverability, and energy efficiency introduces design complexities of the UAVs. For example, due to current design limitations, design tradeoffs exist between optimizing UAVs for high agility versus high energy efficiency. Likewise, aerial vehicles are designed to only operate with four degrees of freedom—pitch, yaw, roll, and heave. In addition, aerial vehicles are generally designed assuming a fully operational state. Accordingly, there is a need for systems and methods to maintain control and safety of aerial vehicles even in degraded operational states.

BRIEF DESCRIPTION OF THE DRAWINGS

The detailed description is described with reference to the accompanying figures. In the figures, the left-most digit(s) of a reference number identifies the figure in which the reference number first appears. The use of the same reference numbers in different figures indicates similar or identical components or features.

FIGS. 1-4 illustrate various views of an aerial vehicle with a substantially hexagonal shaped ring wing, in accordance with disclosed implementations.

FIG. 5 illustrates a view of an adjustable wing section of an aerial vehicle, in accordance with disclosed implementations.

FIG. 6 illustrates a plan view of an aerial vehicle with adjustable wing sections in a first reconfiguration, in accordance with disclosed implementations.

FIG. 7 illustrates a plan view of an aerial vehicle with adjustable wing sections in a second reconfiguration, in accordance with disclosed implementations.

FIGS. 8A-8C illustrate various side views of an aerial vehicle with adjustable wing sections in various reconfigurations, in accordance with disclosed implementations.

FIG. 9A illustrates a plan view of an aerial vehicle with adjustable wing sections in a third reconfiguration, in accordance with disclosed implementations.

FIG. 9B illustrates a plan view of an aerial vehicle with adjustable wing sections in a fourth reconfiguration, in accordance with disclosed implementations.

FIGS. 10A and 10B illustrate various side views of an aerial vehicle with adjustable wing sections in various reconfigurations, in accordance with disclosed implementations.

FIG. 11 illustrates a flow diagram of an example aerial vehicle motor out control process, in accordance with disclosed implementations.

FIG. 12 illustrates a flow diagram of an example aerial vehicle wing reconfiguration process, in accordance with disclosed implementations.

FIG. 13 is a block diagram illustrating various components of an example aerial vehicle control system, in accordance with disclosed implementations.

While implementations are described herein by way of example, those skilled in the art will recognize that the implementations are not limited to the examples or drawings described. It should be understood that the drawings and detailed description thereto are not intended to limit implementations to the particular form disclosed but, on the contrary, the intention is to cover all modifications, equivalents and alternatives falling within the spirit and scope as defined by the appended claims. The headings used herein are for organizational purposes only and are not meant to be used to limit the scope of the description or the claims. As used throughout this application, the word “may” is used in a permissive sense (i.e., meaning having the potential to), rather than the mandatory sense (i.e., meaning must). Similarly, the words “include,” “including,” and “includes” mean including, but not limited to.

DETAILED DESCRIPTION

This disclosure describes aerial vehicles, such as UAVs (e.g., quad-copters, hex-copters, hepta-copters, octa-copters) that can operate in a vertical takeoff and landing (VTOL) orientation or in a horizontal flight orientation. Likewise, when the aerial vehicle is in a VTOL orientation, it can transition independently in any of the six degrees of freedom. Specifically, as described herein, the aerial vehicles may efficiently rotate in any of the three degrees of freedom of rotation (pitch, yaw, and roll) and/or may efficiently move in any of the three degrees of freedom of translation (surge, heave, and sway). For example, the aerial vehicle may include six propulsion mechanisms that are oriented at different angles and therefore, together, can provide thrust in the vertical direction and/or the horizontal direction when the aerial vehicle is in a VTOL orientation.

As discussed further below, a ring wing is included on the aerial vehicle that surrounds the propulsion mechanisms of the aerial vehicle and provides both protection around the propulsion mechanisms and lift when the aerial vehicle is in the horizontal flight orientation and navigating in a substantially horizontal direction.

In addition, responsive to degraded functional states of aerial vehicles such as motor out situations, the aerial vehicles described herein may implement one or more reconfigurations to maintain control of the aerial vehicles and land the aerial vehicles at safe landing locations. In one example embodiment, an aerial vehicle that has detected a failed propulsion mechanism may reconfigure positions of one or more wing sections of a ring wing. In other example embodiments, an aerial vehicle that has detected a failed propulsion mechanism may reconfigure angular orientations of one or more wing sections of a ring wing. In further example embodiments, an aerial vehicle that has detected a failed propulsion mechanism may reconfigure pitches of one or more wing sections of a ring wing. In still further example embodiments, various combinations of reconfigurations may be implemented, and some of the various combinations may include extending or retracting wing sections, angling wing sections upward or downward, and/or changing pitches of wing sections to alter lift generated by the wing sections.

Moreover, although aerial vehicle reconfigurations of one or more wing sections are described herein generally in the context of degraded functional or operational states of aerial vehicles, in some example embodiments, various of the aerial vehicle reconfigurations may be performed even in fully functional states or other operational states of aerial vehicles. In this manner, the wing sections may be modified as described herein to improve or increase controllability of aerial vehicles even in the absence of any particular faults or failures of one or more components of aerial vehicles.

As used herein, a “materials handling facility” may include, but is not limited to, warehouses, distribution centers, cross-docking facilities, order fulfillment facilities, packaging facilities, shipping facilities, rental facilities, libraries, retail stores, wholesale stores, museums, or other facilities or combinations of facilities for performing one or more functions of materials (inventory) handling. A “delivery location,” as used herein, refers to any location at which one or more inventory items (also referred to herein as a payload) may be delivered. For example, the delivery location may be a person's residence, a place of business, a location within a materials handling facility (e.g., packing station, inventory storage), or any location where a user or inventory is located, etc. Inventory or items may be any physical goods that can be transported using an aerial vehicle. For example, an item carried by a payload of an aerial vehicle discussed herein may be ordered by a customer of an electronic commerce website and aerially delivered by the aerial vehicle to a delivery location.

FIG. 1 illustrates a view of an aerial vehicle 100 with a ring wing that is substantially hexagonal in shape and that surrounds a plurality of propulsion mechanisms, according to disclosed implementations. The aerial vehicle 100 includes six propulsion mechanisms 102-1, 102-2, 102-3, 102-4, 102-5, and 102-6 spaced about the fuselage 110 of the aerial vehicle 100. As discussed above, while the propulsion mechanisms 102 may include motors 101-1, 101-2, 101-3, 101-4, 101-5, and 101-6 and propellers 104-1, 104-2, 104-3, 104-4, 104-5, and 104-6, in other implementations, other forms of propulsion may be utilized as the propulsion mechanisms 102. For example, one or more of the propulsion mechanisms 102 of the aerial vehicle 100 may utilize fans, jets, turbojets, turbo fans, jet engines, and/or the like to maneuver the aerial vehicle. Generally described, a propulsion mechanism 102, as used herein, includes any form of propulsion mechanism that is capable of generating a force sufficient to maneuver the aerial vehicle, alone and/or in combination with other propulsion mechanisms. Furthermore, in selected implementations, propulsion mechanisms (e.g., 102-1, 102-2, 102-3, 102-4, 102-5, and 102-6) may be configured such that their individual orientations may be dynamically modified (e.g., change from vertical to horizontal flight orientation or any position therebetween).

Likewise, while the examples herein describe the propulsion mechanisms being able to generate force in either direction, in some implementations, the propulsion mechanisms may only generate force in a single direction. However, the orientation of the propulsion mechanism may be adjusted so that the force can be oriented in a positive direction, a negative direction, and/or any other direction.

In this implementation, the aerial vehicle 100 also includes a ring wing 107 having a substantially hexagonal shape that extends around and forms the perimeter of the aerial vehicle 100. In the illustrated example, the ring wing has six sections or segments 107-1, 107-2, 107-3, 107-4, 107-5, and 107-6 that are joined at adjacent ends to form the ring wing 107 around the aerial vehicle 100. Each segment of the ring wing 107 has an airfoil shape to produce lift when the aerial vehicle is oriented as illustrated in FIG. 1 and moving in a direction that is substantially horizontal. As illustrated, and discussed further below, the ring wing is positioned at an angle with respect to the fuselage 110 such that the lower segment 107-2 of the ring wing acts as a front wing as it is toward the front of the aerial vehicle when oriented as shown and moving in a horizontal direction. The upper segment 107-1 of the ring wing, which has a longer chord length than the lower segment 107-2 of the ring wing 107, is farther back and thus acts as a rear wing.

The ring wing 107 is secured to the fuselage 110 by motor arms 105. In this example, all six motor arms 105-1, 105-2, 105-3, 105-4, 105-5, and 105-6 are coupled to the fuselage at one end, extend from the fuselage 110 and couple to the ring wing 107 at a second end, thereby securing the ring wing 107 to the fuselage 110. In other implementations, less than all of the motor arms may extend from the fuselage 110 and couple to the ring wing 107. For example, motor arms 105-2 and 105-5 may be coupled to the fuselage 110 at one end and extend outward from the fuselage but not couple to the ring wing 107.

In some implementations, the aerial vehicle may also include one or more stabilizer fins 120 that extend from the fuselage 110 to the ring wing 107. The stabilizer fin 120 may also have an airfoil shape. In the illustrated example, the stabilizer fin 120 extends vertically from the fuselage 110 to the ring wing 107. In other implementations, the stabilizer fin may be at other positions. For example, the stabilizer fin may extend downward from the fuselage between motor arm 105-1 and motor arm 105-6.

In general, one or more stabilizer fins may extend from the fuselage 110, between any two motor arms 105 and couple to an interior of the ring wing 107. For example, stabilizer fin 120 may extend upward between motor arms 105-3 and 105-4, a second stabilizer fin may extend from the fuselage and between motor arms 105-5 and 105-6, and a third stabilizer fin may extend from the fuselage and between motor arms 105-1 and 105-2.

Likewise, while the illustrated example shows the motor arm extending from the fuselage 110 at one end and coupling to the interior of the ring wing 107 at a second end, in other implementations, one or more of the stabilizer fin(s) may extend from the fuselage and not couple to the ring wing or may extend from the ring wing and not couple to the fuselage. In some implementations, one or more stabilizer fins may extend from the exterior of the ring wing 107, one or more stabilizer fins may extend from the interior of the ring wing 107, one or more stabilizer fins may extend from the fuselage 110, and/or one or more stabilizer fins may extend from the fuselage 110 and couple to the interior of the ring wing 107.

The fuselage 110, motor arms 105, stabilizer fin 120, and ring wing 107 of the aerial vehicle 100 may be formed of any one or more suitable materials, such as graphite, carbon fiber, and/or aluminum.

Each of the propulsion mechanisms 102 are coupled to a respective motor arm 105 (or propulsion mechanism arm) such that the propulsion mechanism 102 is substantially contained within the perimeter of the ring wing 107. For example, propulsion mechanism 102-1 is coupled to motor arm 105-1, propulsion mechanism 102-2 is coupled to motor arm 105-2, propulsion mechanism 102-3 is coupled to motor arm 105-3, propulsion mechanism 102-4 is coupled to motor arm 105-4, propulsion mechanism 102-5 is coupled to motor arm 105-5, and propulsion mechanism 102-6 is coupled to motor arm 105-6. In the illustrated example, each propulsion mechanism 102-1, 102-2, 102-3, 102-4, 102-5, and 102-6 is coupled at an approximate mid-point of the respective motor arm 105-1, 105-2, 105-3, 105-4, 105-5, and 105-6 between the fuselage 110 and the ring wing 107. In other embodiments, some propulsion mechanisms 102 may be coupled toward an end of the respective motor arm 105. In other implementations, the propulsion mechanisms may be coupled at other locations along the motor arm. Likewise, in some implementations, some of the propulsion mechanisms may be coupled to a mid-point of the motor arm and some of the propulsion mechanisms may be coupled at other locations along respective motor arms (e.g., closer toward the fuselage 110 or closer toward the ring wing 107).

As illustrated, the propulsion mechanisms 102 may be oriented at different angles with respect to each other. For example, propulsion mechanisms 102-2 and 102-5 are aligned with the fuselage 110 such that the force generated by each of propulsion mechanisms 102-2 and 102-5 is in-line or in the same direction or orientation as the fuselage. In the illustrated example, the aerial vehicle 100 is oriented for horizontal flight such that the fuselage is oriented horizontally in the direction of travel. In such an orientation, the propulsion mechanisms 102-2 and 102-5 provide horizontal forces, also referred to herein as thrusting forces and act as thrusting propulsion mechanisms.

In comparison to propulsion mechanisms 102-2 and 102-5, each of propulsion mechanisms 102-1, 102-3, 102-4, and 102-6 are offset or angled with respect to the orientation of the fuselage 110. When the aerial vehicle 100 is oriented horizontally as shown in FIG. 1 for horizontal flight, the propulsion mechanisms 102-1, 102-3, 102-4, and 102-6 may be used as propulsion mechanisms, providing thrust in a non-horizontal direction to cause the aerial vehicle to pitch, yaw, roll, heave and/or sway. In other implementations, during horizontal flight, the propulsion mechanisms 102-1, 102-3, 102-4, and 102-6 may be disabled such that they do not produce any forces and the aerial vehicle 100 may be propelled aerially in a horizontal direction as a result of the lifting force from the aerodynamic shape of the ring wing 107 and the horizontal thrust produced by the thrusting propulsion mechanisms 102-2 and 102-5.

In some implementations, one or more segments of the ring wing 107 may include ailerons, control surfaces, and/or trim tabs 109 that may be adjusted to control the aerial flight of the aerial vehicle 100. For example, one or more ailerons, control surfaces, and/or trim tabs 109 may be included on the upper segment 107-1 of the ring wing 107 and/or one or more ailerons, control surfaces, and/or trim tabs 109 may be included on the side segments 107-4 and/or 107-3. Further, one or more ailerons, control surfaces, and/or trim tabs 109 may also be included on one or more of the remaining segments 107-2, 107-5, and 107-6. The ailerons, control surfaces, and/or trim tabs 109 may be operable to control the pitch, yaw, and/or roll of the aerial vehicle during horizontal flight when the aerial vehicle 100 is oriented as illustrated in FIG. 1.

The angle of orientation of each of the propulsion mechanism 102-1, 102-2, 102-3, 102-4, 102-5, and 102-6 may vary for different implementations. Likewise, in some implementations, the offset of the propulsion mechanisms 102-1, 102-2, 102-3, 102-4, 102-5, and 102-6 may each be the same, with some oriented in one direction and some oriented in another direction, may each be oriented different amounts, and/or in different directions.

In the illustrated example of FIG. 1, each propulsion mechanism 102-1, 102-2, 102-3, 102-4, 102-5, and 102-6 may be oriented approximately thirty degrees with respect to the position of each respective motor arm 105-1, 105-2, 105-3, 105-4, 105-5, and 105-6. In addition, the direction of orientation of the propulsion mechanisms is such that pairs of propulsion mechanisms are oriented toward one another. For example, propulsion mechanism 102-1 is oriented approximately thirty degrees toward propulsion mechanism 102-6. Likewise, propulsion mechanism 102-2 is oriented approximately thirty degrees in a second direction about the second motor arm 105-2 and oriented toward propulsion mechanism 102-3. Finally, propulsion mechanism 102-4 is oriented approximately thirty degrees in the first direction about the fourth motor arm 105-4 and toward propulsion 102-5. As illustrated, propulsion mechanisms 102-2 and 102-5, which are on opposing sides of the fuselage 110, are aligned and oriented in a same first direction (in this example, horizontal). Propulsion mechanisms 102-3 and 102-6, which are on opposing sides of the fuselage 110, are aligned and oriented in a same second direction, which is angled compared to the first direction. Propulsion mechanisms 102-1 and 102-4, which are on opposing sides of the fuselage 110, are aligned and oriented in a same third direction, which is angled compared to the first direction and the second direction.

FIG. 2 illustrates a side view of the aerial vehicle 200 oriented for vertical takeoff and landing (VTOL), in accordance with disclosed implementations. The aerial vehicle 200 corresponds to the aerial vehicle 100 discussed above with respect to FIG. 1. When oriented as illustrated in FIG. 2, the aerial vehicle may maneuver in any of the six degrees of freedom (pitch, yaw, roll, heave, surge, and sway), thereby enabling VTOL and high maneuverability.

As illustrated, when the aerial vehicle is oriented for VTOL, the motor arms and the ring wing 207 are aligned approximately horizontally and in the same plane. In this orientation, each of the propulsion mechanisms are offset or angled with respect to the horizontal and/or vertical direction. As such, each propulsion mechanism 202, when generating a force, generates a force that includes both a horizontal component and a vertical component. In the illustrated example, each propulsion mechanism is angled approximately thirty degrees with respect to vertical. Likewise, as discussed above, adjacent propulsion mechanisms are angled in opposing directions to form pairs of propulsion mechanisms. For example, propulsion mechanism 202-2 is oriented toward propulsion mechanism 202-3. As discussed further below, angling adjacent propulsion mechanisms toward one another to form pairs of propulsion mechanisms allows horizontal forces from each propulsion mechanism to cancel out such that the pair of propulsion mechanisms can produce a net vertical force. Likewise, if one of the propulsion mechanisms of a pair of propulsion mechanisms is producing a larger force than the other propulsion mechanism of the pair, a net horizontal force will result from the pair of propulsion mechanisms. Accordingly, when the aerial vehicle 200 is oriented for VTOL with angled propulsion mechanisms, as illustrated in FIG. 2, the aerial vehicle can move independently in any of the six degrees of freedom. For example, if the aerial vehicle is to surge in the X direction, it can do so by altering the forces produced by the propulsion mechanisms to generate a net horizontal force in the X direction without having to pitch forward to enable a surge in the X direction.

To enable the fuselage to be oriented horizontally with an offset ring wing 207 during horizontal flight, as illustrated in FIG. 1, the fuselage is rotated at an angle when the aerial vehicle 200 is oriented for VTOL, as illustrated in FIG. 2. In this example the fuselage 210 is angled at approximately thirty degrees from vertical. In other implementations, the amount of rotation from vertical may be greater or less depending on the amount of offset desired for the ring wing 207 when the aerial vehicle 200 is oriented for horizontal flight.

The aerial vehicle may also include one or more landing gears 203 that are extendable to a landing position, as illustrated in FIG. 2. During flight, the landing gear 203 may be retracted into the interior of the ring wing 207 and/or may be rotated up and remain along the trailing edge of the ring wing. In still other examples, the landing gear may be permanently affixed.

The fuselage 210 may be used to house or store one or more components of the aerial vehicle, such as the aerial vehicle control system 214, a power module 206, and/or a payload 212 that is transported by the aerial vehicle. The aerial vehicle control system is discussed further below. The power module(s) 206 may be removably mounted to the aerial vehicle 200. The power module(s) 206 for the aerial vehicle may be, for example, in the form of battery power, solar power, gas power, super capacitor, fuel cell, alternative power generation source, or a combination thereof. The power module(s) 206 are coupled to and provide power for the aerial vehicle control system 214, the propulsion mechanisms 202, and the payload engagement module 210-1.

In some implementations, one or more of the power modules may be configured such that it can be autonomously removed and/or replaced with another power module. For example, when the aerial vehicle lands at a delivery location, relay location and/or materials handling facility, the aerial vehicle may engage with a charging member at the location that will recharge the power module.

The payload 212 may be any payload that is to be transported by the aerial vehicle. In some implementations, the aerial vehicle may be used to aerially deliver items ordered by customers for aerial delivery and the payload may include one or more customer ordered items. For example, a customer may order an item from an electronic commerce website and the item may be delivered to a customer specified delivery location using the aerial vehicle 200.

In some implementations, the fuselage 210 may include a payload engagement module 210-1. For example, the payload engagement module 210-1 may be a hinged portion of the fuselage 210 that can rotate between an open position, in which the interior of the fuselage is accessible so that the payload 212 may be added to or removed from the fuselage, and a closed position, as illustrated in FIG. 2, so that the payload 212 is secured within the interior of the fuselage.

FIG. 3 is a side view of an aerial vehicle 300 with a ring wing 307, in accordance with disclosed implementations. The aerial vehicle 300 corresponds to the aerial vehicle 100 discussed in FIG. 1 and aerial vehicle 200 discussed in FIG. 2. As illustrated, when the aerial vehicle is oriented for horizontal flight, as illustrated in FIG. 3, the fuselage 310 is oriented horizontally and two of the propulsion mechanisms, propulsion mechanism 302-2 and the propulsion mechanism on the opposing side of the fuselage and illustrated in FIG. 1, are oriented to produce thrust in a substantially horizontal direction. In comparison, the other propulsion mechanisms, such as propulsion mechanisms 302-1 and 302-3, are not oriented to produce forces in substantially the horizontal direction. During horizontal flight, the propulsion mechanisms, such as propulsion mechanism 302-1 and 302-3, may be disabled and/or used to produce maneuverability forces that will cause the aerial vehicle to pitch, yaw, and/or roll as it aerially navigates in a substantially horizontal direction. In some implementations, the propulsion mechanisms that are not aligned to produce substantially horizontal forces may be allowed to freely rotate in the wind and energy produced from the rotation may be used to charge the power module of the aerial vehicle 300.

The ring wing 307 is angled such that the lower segment 307-2 of the ring wing is positioned ahead of the upper segment 307-1 of the ring wing 307. The leading wing, lower segment 307-2 produces a much higher lift per square inch than the rear wing, upper segment 307-1, and the chord length of the lower segment 307-2 is less than the chord length of the upper segment 307-1. Likewise, as illustrated, the upper segment 307-1 of the ring wing has a different camber than the lower segment 307-2. The chord length and camber transition from that illustrated along the upper segment 307-1 to the lower segment 307-2. In implementations that include one or more stabilizer fins, such as stabilizer fin 120 (FIG. 1), the difference between the chord lengths of the lower segment 307-2 and the upper segment 307-1 may be less and/or the difference between the cambers of the lower segment 307-2 and the upper segment 307-1 may be less.

While the side segments, such as side segment 307-4 and segment 307-6 of the ring wing provide some lift, at the midpoint 308 of each side segment there is minimal lift produced by the ring wing 307. Because there is minimal lift produced at the midpoint 308, the segments may be tapered to reduce the overall weight of the aerial vehicle. In this example, the side segments, such as side segments 307-4 and 307-6, are tapered toward the mid-point but retain some dimension for structural integrity and to operate as a protective barrier around the propulsion mechanisms 302. While the illustrated examples show both side segments 307-4 and 307-6 tapering to a smaller end at the midpoint 308, in other implementations, the taper may be consistent from the larger top segment 307-1 to the smaller lower segment 307-2.

In addition to providing lift, the ring wing 307 provides a protective barrier or shroud that surrounds the propulsion mechanisms of the aerial vehicle 300. The protective barrier of the ring wing 307 increases the safety of the aerial vehicle. For example, if the aerial vehicle comes into contact with another object, there is a higher probability that the object will contact the ring wing, rather than a propulsion mechanism.

FIG. 4 is a front-on view of an aerial vehicle 400 with a ring wing 407 having a substantially hexagonal shape, according to disclosed implementations. The aerial vehicle 400 corresponds to aerial vehicle 100 of FIG. 1, aerial vehicle 200 of FIG. 2, and aerial vehicle 300 of FIG. 3. As discussed above with respect to FIG. 3, when the aerial vehicle is oriented for horizontal flight, as illustrated in FIGS. 3 and 4, the fuselage 410 is oriented in the direction of travel, the ring wing 407 is oriented in the direction of travel such that it will produce a lifting force, and propulsion mechanisms 402-2 and 402-5, which are on opposing sides of the fuselage 410, are aligned to produce forces in the substantially horizontal direction to propel or thrust the aerial vehicle horizontally. The other propulsion mechanisms 402-1, 402-3, 402-4, and 402-6 are offset and may be disabled, used to produce maneuverability forces, and/or allowed to freely rotate and produce energy that is used to charge a power module of the aerial vehicle 400. By increasing the thrust produced by each of the propulsion mechanisms 402-2 and 402-5, the horizontal speed of the aerial vehicle increases. Likewise, the lifting force from the ring wing 407 also increases. In some implementations, one or more ailerons, such as those discussed above with respect to FIG. 1, may be included on the surface of the ring wing and used to control the aerial navigation of the aerial vehicle during horizontal flight. Likewise, one or more stabilizer fins 420 may be included to stabilize the aerial vehicle during horizontal flight.

In some implementations, the hexagonal shaped ring wing may decrease manufacturing costs, provide for more stable flight, and provide flatter surfaces upon which control elements, such as ailerons, may be included, in comparison to a ring wing having a substantially circular shape or various other shapes. Likewise, other components may be coupled to the surface of the ring wing. Other components include, but are not limited to, sensors, imaging elements, range finders, identifying markers, navigation components, such as global positioning satellite antennas, antennas, etc.

As discussed below, to transition the aerial vehicle from a VTOL orientation, as illustrated in FIG. 2, to a horizontal flight orientation, as illustrated in FIGS. 3 and 4, forces generated by each of the propulsion mechanisms 402 will cause the aerial vehicle to pitch forward and increase in speed in the horizontal direction. As the horizontal speed increases and the pitch increases, the lifting force produced by the airfoil shape of the ring wing will increase which will further cause the aerial vehicle to pitch into the horizontal flight orientation and allow the aerial vehicle to remain airborne.

In contrast, as discussed below, when the aerial vehicle is to transition from a horizontal flight orientation to a VTOL orientation, forces from the propulsion mechanisms may cause the aerial vehicle to decrease pitch and reduce horizontal speed. As the pitch of the aerial vehicle decreases, the lift produced by the airfoil shape of the ring wing decreases and the thrust produced by each of the six propulsion mechanisms 402 are utilized to maintain flight of the aerial vehicle 400.

As illustrated in FIGS. 1-4, each of the propulsion mechanisms 402 are positioned in approximately the same plane that is substantially aligned with the ring wing. Likewise, each propulsion mechanism 402 is spaced approximately sixty degrees from each other around the fuselage 410, such that the propulsion mechanisms are positioned at approximately equal distances with respect to one another and around the fuselage 410 of the aerial vehicle 400. For example, the second propulsion mechanism 402-2 and the fifth propulsion mechanism 402-5 may each be positioned along the X axis. The third propulsion mechanism 402-3 may be positioned at approximately sixty degrees from the X axis and the fourth propulsion mechanism 402-4 may be positioned approximately one-hundred and twenty degrees from the X axis. Likewise, the first propulsion mechanism 402-1 and the sixth propulsion mechanism 402-6 may likewise be positioned approximately sixty and one-hundred and twenty degrees from the X axis in the negative direction.

In other implementations, the spacing between the propulsion mechanisms may be different. For example, propulsion mechanisms 402-1, 402-3, and 402-5, which are oriented in the first direction, may each be approximately equally spaced 120 degrees apart and propulsion mechanisms 402-2, 402-4, and 402-6, which are oriented in the second direction, may also be approximately equally spaced 120 degrees apart. However, the spacing between propulsion mechanisms oriented in the first direction and propulsion mechanisms oriented in the second direction may not be equal. For example, the propulsion mechanisms 402-1, 402-3, and 402-5, oriented in the first direction, may be positioned at approximately zero degrees, approximately 120 degrees, and approximately 240 degrees around the perimeter of the aerial vehicle with respect to the X axis, and the propulsion mechanisms 402-2, 402-4, and 402-6, oriented in the second direction, may be positioned at approximately 10 degrees, approximately 130 degrees, and approximately 250 degrees around the perimeter of the aerial vehicle 400 with respect to the X axis.

In other implementations, the propulsion mechanisms may have other alignments. Likewise, in other implementations, there may be fewer or additional propulsion mechanisms. Likewise, in some implementations, the propulsion mechanisms may not all be aligned in the same plane and/or the ring wing may be in a different plane than some or all of the propulsion mechanisms.

While the examples discussed above and illustrated in FIGS. 1-4 discuss rotating the propulsion mechanisms approximately thirty degrees about each respective motor arm and that the ring wing is offset approximately thirty degrees with respect to the fuselage, in other implementations, the orientation of the propulsion mechanisms and/or the ring wing may be greater or less than thirty degrees and the angle of the ring wing may be different than the angle of one or more propulsion mechanisms. In some implementations, if maneuverability of the aerial vehicle when the aerial vehicle is in VTOL orientation is of higher importance, the orientation of the propulsion mechanisms may be higher than thirty degrees. For example, each of the propulsion mechanisms may be oriented approximately forty-five degrees about each respective motor arm, in either the first or second direction. In comparison, if the lifting force of the aerial vehicle when the aerial vehicle is in the VTOL orientation is of higher importance, the orientation of the propulsion mechanisms may be less than thirty degrees. For example, each propulsion mechanism may be oriented approximately ten degrees from a vertical orientation about each respective motor arm.

In some implementations, the orientations of some propulsion mechanisms may be different than other propulsion mechanisms. For example, propulsion mechanisms 402-1, 402-3, and 402-5 may each be oriented approximately fifteen degrees in the first direction and propulsion mechanisms 402-2, 402-4, and 402-6 may be oriented approximately twenty-five degrees in the second direction. In still other examples, pairs of propulsion mechanisms may have different orientations than other pairs of propulsion mechanisms. For example, propulsion mechanisms 402-1 and 402-6 may each be oriented approximately thirty degrees in the first direction and second direction, respectively, toward one another, propulsion mechanisms 402-3 and 402-2 may each be oriented approximately forty-five degrees in the first direction and second direction, respectively, toward one another, and propulsion mechanisms 402-5 and 402-4 may each be oriented approximately forty-five degrees in the first direction and second direction, respectively, toward one another.

As discussed below, by orienting propulsion mechanisms partially toward one another in pairs, as illustrated, the lateral or horizontal forces generated by the pairs of propulsion mechanisms, when producing the same amount of force, will cancel out such that the sum of the forces from the pair is only in a substantially vertical direction (Z direction), when the aerial vehicle is in the VTOL orientation. Likewise, as discussed below, if one propulsion mechanism of the pair produces a force larger than a second propulsion mechanism, a lateral or horizontal force will result in the X direction and/or the Y direction, when the aerial vehicle is in the VTOL orientation. A horizontal force produced from one or more of the pairs of propulsion mechanisms enables the aerial vehicle to translate in a horizontal direction and/or yaw without altering the pitch of the aerial vehicle, when the aerial vehicle is in the VTOL orientation. Producing lateral forces by multiple pairs of propulsion mechanisms 402 enables the aerial vehicle 400 to operate independently in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll). As a result, the stability and maneuverability of the aerial vehicle 400 is increased.

While the implementations illustrated in FIGS. 1-4 include six arms that extend radially from a central portion of the aerial vehicle and are coupled to the ring wing, in other implementations, there may be fewer or additional arms. For example, the aerial vehicle may include support arms that extend between the motor arms and provide additional support to the aerial vehicle. As another example, not all of the motor arms may extend to and couple with the ring wing.

While the examples discussed above in FIGS. 1-4 describe a ring wing in a substantially hexagonal shape, in other implementations, the ring wing may have other shapes. For example, the ring wing may be substantially circular, square, rectangular, pentagonal, octagonal, etc. Further, while the examples discussed above include six propulsion mechanism arms, six propulsion mechanisms, and six propellers, in other example embodiments, the aerial vehicle reconfigurations described herein may be implemented on various other types of aerial vehicles, such as aerial vehicles having fewer than six propulsion mechanism arms, motors, and propellers, aerial vehicles having greater than six propulsion mechanism arms, motors, and propellers, and/or aerial vehicles having configurations different from those described herein, such as quad-copters, octa-copters, or other configurations.

During operation of example aerial vehicles, such as those illustrated and described with respect to FIGS. 1-4, various types of faults or failure modes may arise that result in degraded operational states of the aerial vehicles. For example, one or more of the propulsion mechanisms may no longer operate normally due to various types of faults, which may be referred to as motor out situations. In order to improve the reliability, safety, and operational capability of the aerial vehicles, the aerial vehicles may implement one or more reconfigurations in response to such faults in order to maintain flight of the aerial vehicles and land at safe landing locations.

The various types of faults that may result in motor out situations may include damage or loss of function of one or more propellers or propeller blades, damage or loss of function of one or more motors, damage or loss of function of one or more motor controllers that are each in communication with a corresponding motor and propeller, damage or loss of function between one or more motor controllers and a flight controller that is in communication with each of the motor controllers, loss of power or other electrical signals between two or more components of the aerial vehicle, or various other types of faults.

In addition, the various types of faults may be detected in various manners. For example, damage or loss of function of one or more propellers or propeller blades may be detected by comparison of actual values of motor revolutions per minute (rpm) and applied current with expected values of motor rpm and applied current, since a motor rotating with damaged or missing propellers or blades may draw different values of current than expected values while rotating at a particular motor rpm. In addition, damage or loss of function of one or more motors may be detected by comparison of measured rpm versus commanded rpm, or by measurements and/or calculations related to motor efficiency. Further, various faults of one or more propellers, blades, and/or motors may be detected by one or more motor controllers, which may be provided as feedback to the flight controller. Moreover, various faults of one or more motor controllers may be detected by the flight controller.

In further example embodiments, various other types of sensors may be used to detect one or more of the various types of faults that result in motor out situations. For example, the sensors may include imaging devices or cameras that can capture images of portions of propellers, blades, and/or motors, which images may be processed to determine damage or loss of function of one or more components. In addition, the sensors may include inertial measurement units, accelerometers, gyroscopes, or similar types of sensors that may detect changes to flight operations or navigation of the aerial vehicle that may be caused by one or more faults that result in motor out situations. Various other types of sensors may also detect aspects of flight, navigation, movement, or operation of various components of the aerial vehicles to identify one or more faults. Moreover, the various types of faults may be detected by various combinations of methods described herein.

FIG. 5 illustrates a view of an adjustable wing section of an aerial vehicle, in accordance with disclosed implementations.

As shown in FIG. 5, an aerial vehicle similar to the aerial vehicles described with respect to FIGS. 1-4 is partially illustrated. FIG. 5 illustrates a fuselage 110, a motor arm 105-5, a propulsion mechanism 102-5 coupled to the motor arm 105-5 and including a motor 101-5 and a propeller 104-5, and a wing section 107-5 of a ring wing. In addition, FIG. 5 partially illustrates another wing section 107-3 adjacent to one end of wing section 107-5, and another wing section adjacent to an opposite end of wing section 107-5. Other portions of the aerial vehicle, including other motor arms, propulsion mechanisms, wing sections of the ring wing, and/or stabilizer fins are not illustrated for clarity.

The wing section 107-5 may be reconfigured between a position as illustrated in FIG. 5 in which the wing section 107-5 is connected to adjacent wing sections to form a ring wing as described herein, and one or more other positions in which at least one of an angular orientation, a position, and/or a pitch of the wing section may be modified from the position illustrated in FIG. 5.

For example, the wing section 107-5 may include a releasable or frangible connection 523-3 to an adjacent wing section 107-3 adjacent one end of wing section 107-5, and may include a releasable or frangible connection 523-5 to another wing section adjacent an opposite end of wing section 107-5. In example embodiments, the releasable or frangible connections 523 may comprise one or more magnetic or electromagnetic connections, mechanically releasable connections (such as pin and groove connections, hook and loop connections, keyed connections, threaded connections, or other mechanically releasable connections), physically deformable connections (such as perforated connections, adhesive connections, separable connections that may be heated, melted, torn, or otherwise separated, or other physically deformable connections), or other types of releasable or frangible connections.

In addition, the releasable or frangible connections 523-3, 523-5 may have respective associated actuators 524-3, 524-5 that are configured to cause release or separation of adjacent wing sections. Each of the actuators 524 may be connected via electrical lines or wirelessly (not shown) to an aerial vehicle control system, a part thereof, or another component in communication with the aerial vehicle control system, in order to receive power and/or instructions or commands. In example embodiments, the actuators 524 may comprise one or more magnets or electromagnets to release magnetic or electromagnetic connections. In other example embodiments, the actuators 524 may comprise one or more of a clutch, a switch, a bias element or spring, a damper, a spring-loaded actuator, a servo, a solenoid, a motor, a screw actuator, a geared actuator, a magnetic actuator, a linear actuator, a rotary actuator, a piezoelectric actuator, or various other types of actuators to release mechanically releasable connections. In further example embodiments, the actuators 524 may comprise one or more of a heating element, a conductive element, or various of the other actuators described herein to release physically deformable connections. The actuators 524 may be configured for one-time actuation, e.g., upon detection of a propulsion mechanism failure or other aerial vehicle fault or failure, may be configured for one-way or two-way actuation, may be configured for binary actuation between two different states or positions, and/or may be configured for variable actuation between a plurality of different states or positions. Various combinations of actuators may also be used to cause release or separation of a wing section from one or more adjacent wing sections.

As illustrated in FIG. 5, upon releasing or separating wing section 107-5 from adjacent wing sections at releasable or frangible connections 523 using actuators 524, the wing section 107-5 may be reconfigured to have a different position, angular orientation, and/or pitch via a movable, pivotable, or rotatable connection to the motor arm 105-5 of the aerial vehicle. For example, the movable, pivotable, or rotatable connection may comprise one or more ball joints, gimbal connections, hinged connections, telescoping connections, geared connections, movable arms or linkages, or other movable connections.

In example embodiments, the wing section 107-5 may have one or more associated actuators 525-5 that may move, pivot, or rotate the wing section 107-5 to a different position, e.g., extending the wing section 107-5 away from the fuselage or retracting the wing section 107-5 toward the fuselage. In addition, the one or more associated actuators 525-5 may move, pivot, or rotate the wing section 107-5 to a different angular orientation, e.g., rotating the wing section 107-5 within a plane of the ring wing of the aerial vehicle or relative to a plane of the ring wing of the aerial vehicle, e.g., similar to a dihedral or anhedral angle. Further, the one or more associated actuators 525-5 may pivot or rotate the wing section 107-5 to a different pitch, e.g., rotating the wing section 107-5 such that its leading edge (and trailing edge) have a particular orientation. Each of the actuators 525 may be connected via electrical lines or wirelessly (not shown) to an aerial vehicle control system, a part thereof, or another component in communication with the aerial vehicle control system, in order to receive power and/or instructions or commands.

The actuators 525 may include one or more of a clutch, a switch, a bias element or spring, a damper, a spring-loaded actuator, a servo, a solenoid, a motor, a screw actuator, a geared actuator, a magnetic actuator, a linear actuator, a rotary actuator, a piezoelectric actuator, or various other types of actuators. In addition, the actuators 525 may be configured for one-time actuation, e.g., upon detection of a propulsion mechanism failure or other aerial vehicle fault or failure, may be configured for one-way or two-way actuation, may be configured for binary actuation between two different positions, and/or may be configured for variable actuation between a plurality of different positions. Various combinations of actuators may also be used to cause movement, pivoting, and/or rotation of a wing section relative to a motor arm and/or other portions of the aerial vehicle.

As shown in FIG. 5, the actuators 525 may include a clutch, a switch, or a spring-loaded actuator that moves, pivots, or rotates the wing section 107-5 relative to the motor arm 105-5 between two or more positions, angular orientations, and/or pitches. In addition, the actuators 525 may include a servo or a magnetic actuator that moves, pivots, or rotates the wing section 107-5 relative to the motor arm 105-5 between two or more positions, angular orientations, and/or pitches. Further, the actuators 525 may include a solenoid and a bias element that move, pivot, or rotate the wing section 107-5 relative to the motor arm 105-5 between two or more positions, angular orientations, and/or pitches. Moreover, the actuators 525 may include a motor, a rotary actuator, a screw actuator, a linear actuator, or a geared actuator that moves, pivots, or rotates the wing section 107-5 relative to the motor arm 105-5 between two or more positions, angular orientations, and/or pitches. Various other actuators or combinations of actuators may be used to effect movement, pivoting, and/or rotation of the wing section 107-5 relative to the motor arm 105-5 or other portions of the aerial vehicle.

Although the description here with respect to FIG. 5 relates to only a single wing section 107-5 of the ring wing for clarity, other wing sections of the ring wing of the aerial vehicle may include any and all of the features, components, and/or functions described herein with respect to wing section 107-5. In addition, although FIG. 5 shows particular numbers, arrangements, and orientations of releasable or frangible connections 523, actuators 524, and actuators 525 of the aerial vehicle, various other numbers, arrangements, and orientations of these features may be possible while still providing the described functionality. For example, releasable or frangible connections may be located at other points along the wing sections, actuators to release or separate the releasable or frangible connections may be located in the fuselage or other portions of the aerial vehicle with cables, wires, or other components routed to the releasable or frangible connections to effect release or separation, e.g., by mechanical movement, heat, electrical current, or others, and actuators to reconfigure wing sections may also be located in the fuselage or other portions of the aerial vehicle with cables, wires, or other components routed to the movable connections to effect reconfiguration of the wing sections. Moreover, although FIG. 5 generally describes a single wing section that may be released and associated with a single respective motor arm or portion of the aerial vehicle, in other example embodiments, a single motor arm may be associated with two movable, pivotable, or rotatable wing sections, and/or a different motor arm may be associated with no movable, pivotable, or rotatable wing sections, such that the associations between wing sections and motor arms may not necessarily be rotationally symmetric around the aerial vehicle.

Accordingly, upon detection of a propulsion mechanism failure or other aerial vehicle fault or failure, one or more wing sections of a ring wing of an aerial vehicle may be released or separated from adjacent wing sections via releasable or frangible connections 523 and associated actuators 524. In addition, the one or more wing sections may be moved, pivoted, or rotated to a different position, angular orientation, and/or pitch via movable, pivotable, or rotatable connections of the one or more wing sections with other portions of the aerial vehicle and associated actuators 525. As a result, one or more wing sections of an aerial vehicle may be reconfigured to a different position, angular orientation, and/or pitch to maintain control and safety of the aerial vehicle even in a degraded operational state.

FIG. 6 illustrates a plan view of an aerial vehicle with adjustable wing sections in a first reconfiguration, in accordance with disclosed implementations.

As shown in FIG. 6, responsive to a detected failure or fault of a propulsion mechanism of the aerial vehicle, the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 of the ring wing 107 may be reconfigured to respective extended positions. For example, each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may release or separate from adjacent wing sections, and each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may move, pivot, or rotate to a respective extended position to maximize the overall size or span of the aerial vehicle. In addition, each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may pivot or rotate to a respective angular orientation and/or respective pitch.

In the extended or expanded reconfiguration shown in FIG. 6, the aerial vehicle as a whole may rotate or spin, e.g., approximately around a center of mass of the aerial vehicle. By positioning and/or orienting the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 with particular positions, angular orientations, and/or pitches, the spinning aerial vehicle may generate lift via the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 that may slow a descent of the spinning aerial vehicle and may maintain control and safety of the aerial vehicle. In addition, one or more propulsion mechanisms may also be modified to various angular orientations to facilitate and/or control spinning of the aerial vehicle.

FIG. 7 illustrates a plan view of an aerial vehicle with adjustable wing sections in a second reconfiguration, in accordance with disclosed implementations.

As shown in FIG. 7, responsive to a detected failure or fault of a propulsion mechanism of the aerial vehicle, the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 of the ring wing 107 may be reconfigured to respective partially extended positions. For example, each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may release or separate from adjacent wing sections, and each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may move, pivot, or rotate to a respective partially extended position to increase the overall size or span of the aerial vehicle. In addition, each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may pivot or rotate to a respective angular orientation and/or respective pitch.

In the partially extended or expanded reconfiguration shown in FIG. 7, the aerial vehicle as a whole may rotate or spin, e.g., approximately around a center of mass of the aerial vehicle. By positioning and/or orienting the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 with particular positions, angular orientations, and/or pitches, the spinning aerial vehicle may generate lift via the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 that may slow a descent of the spinning aerial vehicle and may maintain control and safety of the aerial vehicle. In addition, one or more propulsion mechanisms may also be modified to various angular orientations to facilitate and/or control spinning of the aerial vehicle.

FIGS. 8A-8C illustrate various side views of an aerial vehicle with adjustable wing sections in various reconfigurations, in accordance with disclosed implementations.

As shown in FIG. 8A-8C, responsive to a detected failure or fault of a propulsion mechanism of the aerial vehicle, the wing sections 107 of the ring wing may be reconfigured to respective extended positions with various angular orientations. For example, each wing section 107 may release or separate from adjacent wing sections, and each wing section 107 may move, pivot, or rotate to a respective extended position to increase the overall size or span of the aerial vehicle. As shown in FIG. 8A, the wing sections 107 may have an angular orientation that is within a plane of the aerial vehicle. As shown in FIG. 8B, the wing sections 107 may have an angular orientation that is rotated upward relative to a plane of the aerial vehicle, e.g., similar to a dihedral angle. As shown in FIG. 8C, the wing sections 107 may have an angular orientation that is rotated downward relative to a plane of the aerial vehicle, e.g., similar to an anhedral angle.

In the extended or expanded reconfigurations shown in FIGS. 8A-8C, the aerial vehicle as a whole may rotate or spin, e.g., approximately around a center of mass of the aerial vehicle. By positioning and/or orienting the wing sections 107 with particular positions, angular orientations, and/or pitches, the spinning aerial vehicle may generate lift via the wing sections 107 that may slow a descent of the spinning aerial vehicle and may maintain control and safety of the aerial vehicle. In addition, one or more propulsion mechanisms may also be modified to various angular orientations to facilitate and/or control spinning of the aerial vehicle.

FIG. 9A illustrates a plan view of an aerial vehicle with adjustable wing sections in a third reconfiguration, in accordance with disclosed implementations.

As shown in FIG. 9A, responsive to a detected failure or fault of a propulsion mechanism of the aerial vehicle, the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 of the ring wing 107 may be reconfigured to respective retracted positions. For example, each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may release or separate from adjacent wing sections, and each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may move, pivot, or rotate to a respective retracted position to minimize the overall size or span of the aerial vehicle. In addition, each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may pivot or rotate to a respective angular orientation and/or respective pitch.

In the retracted reconfiguration shown in FIG. 9A, the aerial vehicle as a whole may rotate or spin, e.g., approximately around a center of mass of the aerial vehicle. By positioning and/or orienting the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 with particular positions, angular orientations, and/or pitches, the spinning aerial vehicle may generate lift via the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 that may slow a descent of the spinning aerial vehicle and may maintain control and safety of the aerial vehicle. In addition, one or more propulsion mechanisms may also be modified to various angular orientations to facilitate and/or control spinning of the aerial vehicle.

FIG. 9B illustrates a plan view of an aerial vehicle with adjustable wing sections in a fourth reconfiguration, in accordance with disclosed implementations.

As shown in FIG. 9B, responsive to a detected failure or fault of a propulsion mechanism of the aerial vehicle, the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 of the ring wing 107 may be reconfigured to respective partially retracted positions. For example, each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may release or separate from adjacent wing sections, and each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may move, pivot, or rotate to a respective retracted position to reduce the overall size or span of the aerial vehicle. In addition, each wing section 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 may pivot or rotate to a respective angular orientation and/or respective pitch.

In the partially retracted reconfiguration shown in FIG. 9B, the aerial vehicle as a whole may rotate or spin, e.g., approximately around a center of mass of the aerial vehicle. By positioning and/or orienting the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 with particular positions, angular orientations, and/or pitches, the spinning aerial vehicle may generate lift via the wing sections 107-1, 107-2, 107-3, 107-4, 107-5, 107-6 that may slow a descent of the spinning aerial vehicle and may maintain control and safety of the aerial vehicle. In addition, one or more propulsion mechanisms may also be modified to various angular orientations to facilitate and/or control spinning of the aerial vehicle.

FIGS. 10A and 10B illustrate various side views of an aerial vehicle with adjustable wing sections in various reconfigurations, in accordance with disclosed implementations.

As shown in FIGS. 10A and 10B, responsive to a detected failure or fault of a propulsion mechanism of the aerial vehicle, the wing sections 107 of the ring wing may be reconfigured to respective retracted positions with various angular orientations. For example, each wing section 107 may release or separate from adjacent wing sections, and each wing section 107 may move, pivot, or rotate to a respective retracted position to decrease the overall size or span of the aerial vehicle. As shown in FIG. 10A, the wing sections 107 may have an angular orientation that is rotated upward relative to a plane of the aerial vehicle, e.g., similar to a dihedral angle. As shown in FIG. 10B, the wing sections 107 may have an angular orientation that is rotated downward relative to a plane of the aerial vehicle, e.g., similar to an anhedral angle.

In the retracted reconfigurations shown in FIGS. 10A and 10B, the aerial vehicle as a whole may rotate or spin, e.g., approximately around a center of mass of the aerial vehicle. By positioning and/or orienting the wing sections 107 with particular positions, angular orientations, and/or pitches, the spinning aerial vehicle may generate lift via the wing sections 107 that may slow a descent of the spinning aerial vehicle and may maintain control and safety of the aerial vehicle. In addition, one or more propulsion mechanisms may also be modified to various angular orientations to facilitate and/or control spinning of the aerial vehicle.

Although FIGS. 6-10B describe various individual reconfigurations of wing sections of an aerial vehicle such as modifications to positions, angular orientations, or pitches, in various example embodiments, each wing section of an aerial vehicle may be modified with any combination of changes to positions, angular orientations, and/or pitches. Further, although FIGS. 6-10B generally describe the same or similar modifications to positions, angular orientations, and/or pitches of each of the wing sections of an aerial vehicle, in various example embodiments, each wing section of an aerial vehicle may be modified differently from other wing sections of the aerial vehicle. By various combinations of modifications to positions, angular orientations, and/or pitches of one or more wing sections of an aerial vehicle, control and safety of the aerial vehicle may be improved or increased responsive to various potential faults or failures associated with one or more propulsion mechanisms of an aerial vehicle.

In addition, in some example embodiments as shown in FIGS. 6-10B, one or more remaining propulsion mechanisms 102-1, 102-2, 102-3, 102-4, 102-5, 102-6 that have not experienced a fault or failure may also be used to generate lift to further slow a descent of the spinning aerial vehicle. Further, one or more remaining propulsion mechanisms 102-1, 102-2, 102-3, 102-4, 102-5, 102-6 that have not experienced a fault or failure may also be used to generate thrust to allow control and maneuverability, e.g., translation or rotation about various axes, of the spinning aerial vehicle. For example, one or more remaining propulsion mechanisms 102-1, 102-2, 102-3, 102-4, 102-5, 102-6 that have not experienced a fault or failure may also be modified to various angular orientations to facilitate and/or control spinning of the aerial vehicle. Moreover, one or more remaining propulsion mechanisms 102-1, 102-2, 102-3, 102-4, 102-5, 102-6 that have not experienced a fault or failure may also be used to generate thrust as an aerodynamic braking force, e.g., to slow a descent and/or to slow a rate of spin, just prior to landing of the spinning aerial vehicle.

FIG. 11 illustrates a flow diagram of an example aerial vehicle motor out control process 1100, in accordance with disclosed implementations.

The process 1100 may begin by detecting a motor/propeller failure on an aerial vehicle, as at 1102. For example, the motor/propeller failure may be a propulsion mechanism failure. In addition, the detected failure may be any of the various types of faults that may result in motor out situations, as described herein.

The process 1100 may continue by determining whether the aerial vehicle is currently in wingborn flight, as at 1104. For example, wingborn flight may be synonymous with navigation of the aerial vehicle in a substantially horizontal direction, as described with reference to FIGS. 1, 3, and 4. This may be determined based on data associated with the flight controller and/or one or more motor controllers. In addition, this may be determined based on a flight plan of the aerial vehicle. Further, this may be determined based on data associated with one or more sensors, such as an inertial measurement unit, accelerometers, and/or gyroscopes.

If it is determined that the aerial vehicle is currently in wingborn flight, it may then be determined whether the aerial vehicle is to continue wingborn flight, as at 1106. This may be determined based on a flight plan of the aerial vehicle, controllability of the aerial vehicle due to the motor out situation, remaining power or range of the aerial vehicle, additional drag due to the motor out situation, distance to a safe landing location for the aerial vehicle, objects, people, and/or obstacles in an environment of the aerial vehicle, temperature, wind, precipitation, pressure, or other environmental factors, and/or various other factors.

If it is determined that the aerial vehicle is to continue wingborn flight, then the process 1100 may proceed by reconfiguring one or more wing sections for wingborn flight, as at 1108. For example, one or more wing sections may be reconfigured to have modified positions, angular orientations, and/or pitches in order to maintain control and safety of the aerial vehicle in wingborn flight responsive to the motor out situation. For example, positions, angular orientations, and/or pitches of one or more wing sections may be modified to provide additional lift to maintain wingborn flight. The determination of whether to continue with wingborn flight may also be based on a flight plan of the aerial vehicle, controllability of the aerial vehicle due to the motor out situation, remaining power or range of the aerial vehicle, additional drag due to the motor out situation, distance to a safe landing location for the aerial vehicle, objects, people, and/or obstacles in an environment of the aerial vehicle, temperature, wind, precipitation, pressure, or other environmental factors, and/or various other factors.

In an example embodiment, referring to the aerial vehicle illustrated in FIG. 1, wing sections 107-1, 107-2 may be maintained in their positions as shown, wing sections 107-3, 107-4 may be extended to substantially form a line or plane with wing section 107-1, and wing sections 107-5, 107-6 may also be extended to substantially form a line or plane with wing section 107-2, such that the reconfigured aerial vehicle effectively includes one large upper wing and one large lower wing. In this manner, the aerial vehicle may be able to generate greater lift with the reconfigured wing sections 107-3, 107-4, 107-5, 107-6 and continue wingborn flight. In addition, angular orientations and/or pitches of the wing sections may also be modified to increase or adjust lift.

In another example embodiment, referring to the aerial vehicle illustrated in FIG. 1, wing sections 107-1, 107-2, 107-5, 107-6 may be maintained in their positions as shown, and wing sections 107-3, 107-4 may be extended from the far left and far right corners, respectively, of the aerial vehicle, such that the reconfigured aerial vehicle effectively includes one upper wing, one left wing, one right wing, and one lower wing. In this manner, the aerial vehicle may be able to generate greater lift with the reconfigured wing sections 107-3, 107-4 and continue wingborn flight. In addition, angular orientations and/or pitches of the wing sections may also be modified to increase or adjust lift.

In a further example embodiment, referring to the aerial vehicle illustrated in FIG. 1, wing sections 107-1, 107-2, 107-3, 107-4 may be maintained in their positions as shown, and wing sections 107-5, 107-6 may be extended from the far left and far right corners, respectively, of the aerial vehicle, such that the reconfigured aerial vehicle effectively includes one upper wing, one left wing, one right wing, and one lower wing. In this manner, the aerial vehicle may be able to generate greater lift with the reconfigured wing sections 107-5, 107-6 and continue wingborn flight. In addition, angular orientations and/or pitches of the wing sections may also be modified to increase or adjust lift.

After reconfiguring the wing sections and continuing wingborn flight, as at 1108, the process 1100 may then continue by determining whether to transition to VTOL flight, as at 1110. The determination of whether to transition to VTOL flight may also be based on a flight plan of the aerial vehicle, controllability of the aerial vehicle due to the motor out situation, remaining power or range of the aerial vehicle, additional drag due to the motor out situation, distance to a safe landing location for the aerial vehicle, objects, people, and/or obstacles in an environment of the aerial vehicle, temperature, wind, precipitation, pressure, or other environmental factors, and/or various other factors.

If it is determined that the aerial vehicle is to transition to VTOL flight, as at 1110, or after determining that the aerial vehicle is not to continue in wingborn flight, as at 1106, then the process 1100 may proceed to transition the aerial vehicle from wingborn flight to VTOL flight using any control surfaces and/or any remaining propulsion mechanisms, as at 1112. As described herein, the aerial vehicle may transition from wingborn flight to VTOL flight by reducing pitch and/or speed of the aerial vehicle such that the ring wing produces less lift and the aerial vehicle pitches rearward to a VTOL flight orientation, as described with respect to FIG. 2.

After transitioning to VTOL flight, as at 1112, or after determining that the aerial vehicle is not currently in wingborn flight, as at 1104, the process 1100 may continue by reconfiguring one or more wing sections for VTOL flight, as at 1114. For example, one or more wing sections may be reconfigured to have modified positions, angular orientations, and/or pitches in order to maintain control and safety of the aerial vehicle in VTOL flight responsive to the motor out situation. For example, positions of one or more wing sections may be extended or retracted to modify the size of span of the aerial vehicle in VTOL flight. In addition, angular orientations of one or more wing sections may be modified to pivot or rotate relative to a plane of the aerial vehicle. Further, pitches of one or more wing sections may be modified to adjust orientations of their leading and trailing edges, e.g., angle of attack. The various reconfigurations of the wing sections may cause the aerial vehicle as a whole to rotate or spin, and the wing sections may be reconfigured to various positions, angular orientations, and/or pitches to generate lift to slow a descent of the aerial vehicle and maintain control and safety of the aerial vehicle.

After reconfiguring one or more wing sections for VTOL flight, as at 1114, or after determining that the aerial vehicle is not to transition to VTOL flight and instead continue with wingborn flight, as at 1110, the process 1100 may proceed by identifying a safe landing location, as at 1116. For example, the safe landing location may be predetermined and stored by or provided to the aerial vehicle. Various safe landing locations may be identified and stored beforehand, and the aerial vehicle may identify a closest available safe landing location responsive to the motor out situation. In other examples, the aerial vehicle may use one or more sensors, such as imaging devices, radar, LIDAR, proximity sensors, inertial measurement units, navigation sensors such as global positioning sensors, and/or other types of sensors, to identify a safe landing location responsive to the motor out situation. Various other types of sensors, beacons, or communication devices may also be used to identify a safe landing location for the aerial vehicle.

The process 1100 may then continue to control the aerial vehicle using the reconfigured one or more wing sections to the safe landing location, as at 1118. For example, the aerial vehicle may reconfigure one or more wing sections for wingborn flight and/or may reconfigure one or more wing sections for VTOL flight, and the aerial vehicle may navigate to the identified safe landing location using the reconfigured one or more wing sections, as well as based on data from one or more sensors, such as imaging devices and navigation sensors. The process 1100 may then end, as at 1120.

FIG. 12 illustrates a flow diagram of an example aerial vehicle wing reconfiguration process 1200, in accordance with disclosed implementations.

The process 1200 may begin by determining whether to modify positions of one or more wing sections, as at 1202. If it is determined that positions of one or more wing sections are to be modified responsive to a motor out situation, then the process 1200 may continue to control one or more actuators to modify positions of associated wing sections, as at 1204. As described herein, various types, numbers, or arrangements of actuators may be associated with each of the one or more wing sections, and one or more of such actuators may be actuated to effect changes to positions of the associated wing sections, e.g., extended away from the fuselage, or retracted toward the fuselage.

The process 1200 may then proceed by determining whether to modify angular orientations of one or more wing sections, as at 1206. If it is determined that angular orientations of one or more wing sections are to be modified responsive to a motor out situation, then the process 1200 may continue to control one or more actuators to modify angular orientations of associated wing sections, as at 1208. As described herein, various types, numbers, or arrangements of actuators may be associated with each of the one or more wing sections, and one or more of such actuators may be actuated to effect changes to angular orientations of associated wing sections, e.g., relative to a plane of the aerial vehicle.

The process 1200 may then proceed by determining whether to modify pitches of one or more wing sections, as at 1210. If it is determined that pitches of one or more wing sections are to be modified responsive to a motor out situation, then the process 1200 may continue to control one or more actuators to modify pitches of associated wing sections, as at 1212. As described herein, various types, numbers, or arrangements of actuators may be associated with each of the one or more wing sections, and one or more of such actuators may be actuated to effect changes to pitches of the associated wing sections, e.g., to affect an amount of lift generated by each wing section as part of the reconfigured aerial vehicle.

FIG. 13 is a block diagram illustrating various components of an example aerial vehicle control system 1300, in accordance with disclosed implementations.

In various examples, the block diagram may be illustrative of one or more aspects of the aerial vehicle control system 1300 that may be used to implement the various systems and methods discussed herein and/or to control operation of an aerial vehicle discussed herein. In the illustrated implementation, the aerial vehicle control system 1300 includes one or more processors 1302, coupled to a memory, e.g., a non-transitory computer readable storage medium 1320, via an input/output (I/O) interface 1310. The aerial vehicle control system 1300 also includes propulsion mechanism controllers 1304, such as electronic speed controls (ESCs) or motor controllers, power modules 1306 and/or a navigation system 1307. The aerial vehicle control system 1300 further includes a payload engagement controller 1312, a control module 1313 configured to implement one or more aerial vehicle reconfigurations described herein, a network interface 1316, and one or more input/output devices 1317.

In various implementations, the aerial vehicle control system 1300 may be a uniprocessor system including one processor 1302, or a multiprocessor system including several processors 1302 (e.g., two, four, eight, or another suitable number). The processor(s) 1302 may be any suitable processor capable of executing instructions. For example, in various implementations, the processor(s) 1302 may be general-purpose or embedded processors implementing any of a variety of instruction set architectures (ISAs), such as the x86, PowerPC, SPARC, or MIPS ISAs, or any other suitable ISA. In multiprocessor systems, each processor(s) 1302 may commonly, but not necessarily, implement the same ISA.

The non-transitory computer readable storage medium 1320 may be configured to store executable instructions, data, flight paths, flight control parameters, center of gravity information, and/or data items accessible by the processor(s) 1302. In various implementations, the non-transitory computer readable storage medium 1320 may be implemented using any suitable memory technology, such as static random access memory (SRAM), synchronous dynamic RAM (SDRAM), nonvolatile/Flash-type memory, or any other type of memory. In the illustrated implementation, program instructions and data implementing desired functions, such as those described herein, are shown stored within the non-transitory computer readable storage medium 1320 as program instructions 1322, data storage 1324 and flight controls 1326, respectively. In other implementations, program instructions, data, and/or flight controls may be received, sent, or stored upon different types of computer-accessible media, such as non-transitory media, or on similar media separate from the non-transitory computer readable storage medium 1320 or the aerial vehicle control system 1300. Generally speaking, a non-transitory, computer readable storage medium may include storage media or memory media such as magnetic or optical media, e.g., disk or CD/DVD-ROM, coupled to the aerial vehicle control system 1300 via the I/O interface 1310. Program instructions and data stored via a non-transitory computer readable medium may be transmitted by transmission media or signals such as electrical, electromagnetic, or digital signals, which may be conveyed via a communication medium such as a network and/or a wireless link, such as may be implemented via the network interface 1316.

In one implementation, the I/O interface 1310 may be configured to coordinate I/O traffic between the processor(s) 1302, the non-transitory computer readable storage medium 1320, and any peripheral devices, the network interface or other peripheral interfaces, such as input/output devices 1317. In some implementations, the I/O interface 1310 may perform any necessary protocol, timing or other data transformations to convert data signals from one component (e.g., non-transitory computer readable storage medium 1320) into a format suitable for use by another component (e.g., processor(s) 1302). In some implementations, the I/O interface 1310 may include support for devices attached through various types of peripheral buses, such as a variant of the Peripheral Component Interconnect (PCI) bus standard or the Universal Serial Bus (USB) standard, for example. In some implementations, the function of the I/O interface 1310 may be split into two or more separate components, such as a north bridge and a south bridge, for example. Also, in some implementations, some or all of the functionality of the I/O interface 1310, such as an interface to the non-transitory computer readable storage medium 1320, may be incorporated directly into the processor(s) 1302.

The propulsion mechanism controllers 1304 may communicate with the navigation system 1307 and adjust the rotational speed, position, orientation, or other parameters of each propulsion mechanism to implement one or more aerial vehicle reconfigurations, to stabilize the aerial vehicle, and/or to perform one or more maneuvers and guide the aerial vehicle along a flight path and/or to a safe landing location.

The navigation system 1307 may include a global positioning system (GPS), indoor positioning system (IPS), or other similar system and/or sensors that can be used to navigate the aerial vehicle to and/or from a location. The payload engagement controller 1312 communicates with the actuator(s) or motor(s) (e.g., a servo motor) used to engage and/or disengage items.

The control module 1313 may comprise or form a part of a flight controller that is configured to implement one or more aerial vehicle reconfigurations described herein, such as modifying positions of one or more wing sections, modifying angular orientations of one or more wing sections, modifying pitches of one or more wing sections, or other reconfigurations of the aerial vehicle. Further, the control module 1313 may also be configured to control wingborn or horizontal flight of the aerial vehicle, VTOL flight of the aerial vehicle, and transitions between wingborn and VTOL flight orientations of the aerial vehicle. The control module 1313 may send and/or receive data to/from one or more sensors, such as imaging devices, an inertial measurement unit, accelerometers, gyroscopes, navigation sensors, or other sensors, and/or the control module 1313 may send and/or receive data to/from propulsion mechanism controllers 1304 associated with respective propulsion mechanisms. In some example embodiments, the control module 1313 may be integrated with or form a part of one or more of the processors 1302, the propulsion mechanism controllers 1304, and/or the navigation system 1307.

The network interface 1316 may be configured to allow data to be exchanged between the aerial vehicle control system 1300, other devices attached to a network, such as other computer systems (e.g., remote computing resources), and/or with aerial vehicle control systems of other aerial vehicles. For example, the network interface 1316 may enable wireless communication between the aerial vehicle and an aerial vehicle control system that is implemented on one or more remote computing resources. For wireless communication, an antenna of the aerial vehicle or other communication components may be utilized. As another example, the network interface 1316 may enable wireless communication between numerous aerial vehicles. In various implementations, the network interface 1316 may support communication via wireless general data networks, such as a Wi-Fi network. For example, the network interface 1316 may support communication via telecommunications networks, such as cellular communication networks, satellite networks, and the like.

Input/output devices 1317 may, in some implementations, include one or more displays, imaging devices, thermal sensors, infrared sensors, time of flight sensors, accelerometers, pressure sensors, weather sensors, etc. Multiple input/output devices 1317 may be present and controlled by the aerial vehicle control system 1300. One or more of these sensors may be utilized to implement the aerial vehicle reconfigurations described herein, as well as to detect failures or faults, control wingborn or VTOL flight, effect transitions between wingborn and VTOL configurations, identify safe landing locations, and/or any other operations or functions described herein.

As shown in FIG. 13, the memory may include program instructions 1322, which may be configured to implement the example routines and/or sub-routines described herein. The data storage 1324 may include various data stores for maintaining data items that may be provided for aerial vehicle reconfigurations, determining flight paths, landing, identifying locations for disengaging items, determining which propulsion mechanisms to utilize to execute a maneuver, etc. In various implementations, the parameter values and other data illustrated herein as being included in one or more data stores may be combined with other information not described or may be partitioned differently into more, fewer, or different data structures. In some implementations, data stores may be physically located in one memory or may be distributed among two or more memories.

Those skilled in the art will appreciate that the aerial vehicle control system 1300 is merely illustrative and is not intended to limit the scope of the present disclosure. In particular, the computing system and devices may include any combination of hardware or software that can perform the indicated functions. The aerial vehicle control system 1300 may also be connected to other devices that are not illustrated, or instead may operate as a stand-alone system. In addition, the functionality provided by the illustrated components may, in some implementations, be combined in fewer components or distributed in additional components. Similarly, in some implementations, the functionality of some of the illustrated components may not be provided and/or other additional functionality may be available.

Those skilled in the art will also appreciate that, while various items are illustrated as being stored in memory or storage while being used, these items or portions of them may be transferred between memory and other storage devices for purposes of memory management and data integrity. Alternatively, in other implementations, some or all of the software components may execute in memory on another device and communicate with the illustrated aerial vehicle control system 1300. Some or all of the system components or data structures may also be stored (e.g., as instructions or structured data) on a non-transitory, computer-accessible medium or a portable article to be read by an appropriate drive, various examples of which are described herein. In some implementations, instructions stored on a computer-accessible medium separate from the aerial vehicle control system 1300 may be transmitted to the aerial vehicle control system 1300 via transmission media or signals such as electrical, electromagnetic, or digital signals, conveyed via a communication medium such as a wireless link. Various implementations may further include receiving, sending, or storing instructions and/or data implemented in accordance with the foregoing description upon a computer-accessible medium. Accordingly, the techniques described herein may be practiced with other aerial vehicle control system configurations.

The above aspects of the present disclosure are meant to be illustrative. They were chosen to explain the principles and application of the disclosure and are not intended to be exhaustive or to limit the disclosure. Many modifications and variations of the disclosed aspects may be apparent to those of skill in the art. Persons having ordinary skill in the field of computers, communications, and speech processing should recognize that components and process steps described herein may be interchangeable with other components or steps, or combinations of components or steps, and still achieve the benefits and advantages of the present disclosure. Moreover, it should be apparent to one skilled in the art that the disclosure may be practiced without some or all of the specific details and steps disclosed herein.

While the above examples have been described with respect to aerial vehicles, the disclosed implementations may also be used for other forms of vehicles, including, but not limited to, ground based vehicles and water based vehicles.

Aspects of the disclosed system may be implemented as a computer method or as an article of manufacture such as a memory device or non-transitory computer readable storage medium. The computer readable storage medium may be readable by a computer and may comprise instructions for causing a computer or other device to perform processes described in the present disclosure. The computer readable storage media may be implemented by a volatile computer memory, non-volatile computer memory, hard drive, solid-state memory, flash drive, removable disk and/or other media. In addition, components of one or more of the modules and engines may be implemented in firmware or hardware.

Unless otherwise explicitly stated, articles such as “a” or “an” should generally be interpreted to include one or more described items. Accordingly, phrases such as “a device configured to” are intended to include one or more recited devices. Such one or more recited devices can also be collectively configured to carry out the stated recitations. For example, “a processor configured to carry out recitations A, B and C” can include a first processor configured to carry out recitation A working in conjunction with a second processor configured to carry out recitations B and C.

Language of degree used herein, such as the terms “about,” “approximately,” “generally,” “nearly” or “substantially” as used herein, represent a value, amount, or characteristic close to the stated value, amount, or characteristic that still performs a desired function or achieves a desired result. For example, the terms “about,” “approximately,” “generally,” “nearly” or “substantially” may refer to an amount that is within less than 10% of, within less than 5% of, within less than 1% of, within less than 0.1% of, and within less than 0.01% of the stated amount.

As used throughout this application, the word “may” is used in a permissive sense (i.e., meaning having the potential to), rather than the mandatory sense (i.e., meaning must). Similarly, the words “include,” “including,” and “includes” mean including, but not limited to. Additionally, as used herein, the term “coupled” may refer to two or more components connected together, whether that connection is permanent (e.g., welded) or temporary (e.g., bolted), direct or indirect (e.g., through an intermediary), mechanical, chemical, optical, or electrical. Furthermore, as used herein, “horizontal” flight refers to flight traveling in a direction substantially parallel to the ground (e.g., sea level), and that “vertical” flight refers to flight traveling substantially radially outward from or inward toward the earth's center. It should be understood by those having ordinary skill that trajectories may include components of both “horizontal” and “vertical” flight vectors.

Although the invention has been described and illustrated with respect to illustrative implementations thereof, the foregoing and various other additions and omissions may be made therein and thereto without departing from the spirit and scope of the present disclosure. 

What is claimed is:
 1. An aerial vehicle, comprising: a fuselage; six motor arms coupled to and extending from the fuselage; six motors, each motor coupled to a respective motor arm and positioned around the fuselage; six propellers, each propeller coupled to and rotated by a respective motor; a ring wing comprising six wing sections positioned around the fuselage, the six motors, and the six propellers, a respective spanwise end of each wing section coupled to a respective outer end of a respective motor arm; and six actuators, each actuator coupled to a respective wing section and configured to alter an orientation of the respective wing section about the respective outer end of the respective motor arm.
 2. The aerial vehicle of claim 1, wherein orientations of the six wing sections are configured to be altered to extend the six wing sections away from the fuselage.
 3. The aerial vehicle of claim 1, wherein orientations of the six wing sections are configured to be altered to angle outer ends of the six wing sections upward relative to the fuselage.
 4. The aerial vehicle of claim 1, wherein orientations of the six wing sections are configured to be altered to change pitches of the six wing sections.
 5. The aerial vehicle of claim 1, further comprising: a controller configured to at least: detect a failure of at least one of: a first motor of the six motors, or a first propeller of the six propellers; responsive to the detected failure, actuate at least one actuator of the six actuators to alter an orientation of a respective wing section relative to a respective motor arm; identify a safe landing location for the aerial vehicle; and navigate, at least partially using auto-rotation, the aerial vehicle to the safe landing location.
 6. An aerial vehicle, comprising: a fuselage; a plurality of propulsion mechanism arms coupled to and extending from the fuselage; a plurality of propulsion mechanisms, each propulsion mechanism coupled to a respective propulsion mechanism arm and positioned around the fuselage; a ring wing comprising a plurality of wing sections positioned around the fuselage and the plurality of propulsion mechanisms, a respective spanwise end of each wing section coupled to a respective outer end of a respective propulsion mechanism arm; and a first actuator coupled to a first wing section and configured to alter an orientation of the first wing section about a first outer end of a first propulsion mechanism arm.
 7. The aerial vehicle of claim 6, wherein the first actuator is configured to alter the orientation of the first wing section to at least one of extend or retract the first wing section away from or toward the fuselage.
 8. The aerial vehicle of claim 6, wherein the first actuator is configured to alter the orientation of the first wing section to change an angle of the first wing section relative to the first propulsion mechanism arm.
 9. The aerial vehicle of claim 6, wherein the first actuator is configured to alter the orientation of the first wing section to change a pitch of the first wing section.
 10. The aerial vehicle of claim 6, wherein the first actuator is coupled to the plurality of wing sections and configured to collectively alter orientations of the plurality of wing sections.
 11. The aerial vehicle of claim 6, further comprising: a plurality of actuators, each actuator coupled to a respective wing section and configured to alter an orientation of the respective wing section; wherein the plurality of actuators comprise the first actuator.
 12. The aerial vehicle of claim 11, wherein the plurality of actuators are configured to alter orientations of respective wing sections to form at least one of an upper wing or a lower wing for horizontal flight.
 13. The aerial vehicle of claim 6, wherein the first actuator comprises at least one of a clutch, a switch, a bias element, a servo, a solenoid, a motor, a screw actuator, a magnetic actuator, a linear actuator, or a rotary actuator.
 14. The aerial vehicle of claim 6, further comprising: a controller configured to at least: detect a failure of the first propulsion mechanism of the plurality of propulsion mechanisms; responsive to the detected failure, actuate the first actuator to alter the orientation of the first wing section; identify a safe landing location for the aerial vehicle; and navigate the aerial vehicle to the safe landing location.
 15. A method to control an aerial vehicle, comprising: detecting a failure of a first propulsion mechanism, the aerial vehicle comprising a plurality of propulsion mechanisms associated with a respective plurality of propulsion mechanism arms, a ring wing comprising a plurality of wing sections positioned around the plurality of propulsion mechanisms, and a plurality of actuators, wherein each actuator is associated with a respective wing section of the ring wing, and wherein a respective spanwise end of each wing section is coupled to a respective outer end of a respective propulsion mechanism arm; responsive to the detected failure, actuating at least one actuator of the plurality of actuators to alter an orientation of a respective wing section about a respective outer end of a respective propulsion mechanism arm; identifying a safe landing location for the aerial vehicle; and navigating, at least partially using auto-rotation, the aerial vehicle to the safe landing location.
 16. The method of claim 15, further comprising: responsive to the detected failure, actuating the plurality of actuators to alter orientations of respective wing sections to extend the respective wing sections away from a fuselage of the aerial vehicle.
 17. The method of claim 15, further comprising: responsive to the detected failure, actuating the plurality of actuators to alter orientations of respective wing sections to change angles of the respective wing sections relative to a fuselage of the aerial vehicle to adjust lift generated due to auto-rotation.
 18. The method of claim 15, further comprising: responsive to the detected failure, actuating the plurality of actuators to alter orientations of respective wing sections to change pitches of the respective wing sections to adjust lift generated due to auto-rotation.
 19. The method of claim 15, further comprising: responsive to the detected failure, operating at least one of remaining propulsion mechanisms to maneuver the aerial vehicle to the safe landing location.
 20. The method of claim 15, further comprising: responsive to the detected failure, operating at least one of remaining propulsion mechanisms to slow down the aerial vehicle prior to landing at the safe landing location. 